CN103631255A - Fault injection equipment and method for avionics system health diagnosis - Google Patents
Fault injection equipment and method for avionics system health diagnosis Download PDFInfo
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Abstract
The invention discloses fault injection equipment for avionics system health diagnosis. The equipment comprises an industrial control unit, a waveform generation unit and a signal conditioning unit. The industrial control unit is used for analyzing protocols and encapsulating data according to a fault model. The waveform generation unit is used for finishing data analysis, caching waveform data, performing digital-analog conversion on the waveform data, and outputting generated analog waveform to the signal conditioning unit. The signal conditioning unit is used for re-conditioning the analog waveform and finally outputting electrical signals to an interface connector as required. Possible random/sudden faults in actual work environments are simulated by the equipment, so that the reliability and accuracy of a system under diagnosis is verified in a shortest time, the development, test and productization time of the system is shortened, and costs in non-flight ground maintenance and logistical support are reduced.
Description
Technical field
The invention belongs to aviation electronics technical field of measurement and test.
Background technology
Along with the raising of avionics system complexity, comprehensive coverage and the fault diagnosis ability of maintenance have also been proposed to more and more higher requirement.Method for diagnosing faults is evolved as current prognostics and health management (PHM) system by external testing, built-in test (BIT), from condition monitoring, to health control, change, the predictive ability to the following reliability of system has been introduced in this transformation, generation, Maintenance Planning and supply guarantee by this capability identification and management avionics system fault, its fundamental purpose is to reduce to use and support cost, improve avionics system security, integrity and Mission Success, thereby with less maintenance, drop into, realize the maintenance based on state.At present, PHM has become the inexorable trend of aviation electronics Reliability & Maintainability development of new generation.
The content that PHM comprises two aspects, i.e. prediction and health control, health refers to the hydraulic performance decline of comparing with the normal performance state of expecting or extent of deviation in allowed limits; Failure prediction refers to or historical performance status predication present according to system, and deagnostic package or system complete the state (following health status) of its function, comprise the residual life of determining means or system or the time span of normal operation; Health control is maintenance to be made to the ability of suitable decision-making according to diagnosis/information of forecasting, available Maintenance Resource and request for utilization.PHM system generally should possess following function: fault detect, fault isolation, fault diagnosis, failure prediction, health control and life-span follow the trail of.For complicated Aerial Electronic Equipment and system, PHM should be able to realize comprehensive diagnos, prediction and the health control of different levels, different stage.
The implementation method of Gernral Check-up mainly comprises analysis of failure pattern, mechanism and impact analysis, it has comprised design data, fault mode, failure mechanism, fault model, life cycle section and maintenance record, and sensing data, bus monitoring data and BIT test result are also for determining abnormality and parameter.By fault analysis, carry out targetedly fault injection, determine the contingent pattern of fault and probability.
Fault is injected and is referred to according to prior selected fault model, adopts specific strategy artificially fault to be incorporated in system, with acceleration disturbance and wrong generation.By observation and analysis system in the duty being injected under failure condition, the reliability of evaluating system.
Because fault injection is general direct for goal systems, therefore can avoid producing the inexactness of bringing because model hypothesis is inaccurate of similar analytic method.The design phase of this external goal systems, simulated failure is injected a kind of means that can be used as the behavior of Study system fault, because adopting the object that fault is injected is exactly to lose efficacy in order to accelerate, obtain abundant fail data within a short period of time, so that statistical study.As a kind of effective technology, fault is injected the attention that has caused increasing project planner and researcher.
According to fault, inject the technical method of realizing, the fault that is divided three classes is injected: hardware fault is injected, software fault injects, radiation induced fault is injected.
At present fault is injected as a kind of reliability testing means, is widely used in computing system, chip reliability analytical test, and about aspect the reliability testing of avionics system, fault is injected the research of relevant device and practice in the starting stage both at home and abroad.Therefore, research and develop a kind of resultant fault injection device for avionics system special use, realize avionics system Gernral Check-up tool is of great significance.
Summary of the invention
Goal of the invention of the present invention is to provide a kind of Fault Insertion Equipment for avionics system Gernral Check-up, can introduce that waveform is editable in electrical layer, the resultant fault of multiple types fault-signal injects platform.Utilize in this platform simulation actual working environment may random/catastrophic failure phenomenon, thereby guarantee that checking is by the reliability of diagnostic system and correctness within the shortest time, the research and development of shortening system, test and commercialization time, reduce ground maintenance and logistics support cost under non-state of flight.
Goal of the invention of the present invention is achieved through the following technical solutions:
A kind of Fault Insertion Equipment for avionics system Gernral Check-up, comprise industry control unit, wave generating unit, signal condition unit, described industry control unit injects type according to man-machine interface to various faults and selects, call different faults data-interface model and carry out protocol encapsulation and generate Wave data and deliver to wave generating unit by pci bus, and by RS232 bus to signal condition unit distribution control command and the parameter configuration of signal and the parameter configuration of interference;
Described wave generating unit is received Wave data and is resolved by pci bus, and buffer memory Wave data, carries out digital-to-analog conversion to Wave data, and all kinds of analog signal waveforms of generation and the data model of interference waveform output to signal condition unit;
Signal condition cell processing receives control command and the parameter configuration of signal and the parameter configuration of interference of industry control unit distribution, also receive the various types of signal waveform of wave generating unit and the data model of interference waveform simultaneously, generation meets the data of bus protocol and electric requirement, and being injected into tested equipment by corresponding connector, these data comprise bus data and interfering data etc.
Preferably, described wave generating unit comprises DSP module, FPGA module, DAC module, power module, clock module;
Described DSP module has been used for the interface conversion resolution data between industry control unit and wave generating unit, and data buffer storage;
Described FPGA module comprises buffer memory RAM, asynchronous FIFO and fifo control logic chip, for completing DSP module to interface conversion, the data buffer storage of DAC module and giving DAC by data according to refresh rate undetermined and do digital-to-analog conversion;
Described DAC module has been used for the conversion of digital signal, and analog signal output is arrived to signal condition unit;
Described power module major function is to realize each unit that direct power supply is provided, and it,, by AC-DC power conversion chip, then becomes the required direct supply of each module by voltage stabilizing, filtering, DC-DC circuit conversion;
Described clock module major function is for each module provides clock input, guarantees the signal integrity of transmitting procedure.
Preferably, described signal condition unit comprises signal coupling and distribution module, conditioning plate control module, power module, each signal condition module;
Described power module provides power supply guarantee for each module;
Described signal coupling and distribution module, arrive this unit by the signal coupling of wave generating unit output, and signal be distributed to each signal condition module under the control of conditioning plate control module;
Described signal condition module, nurses one's health conversion to input signal, produces the data that meet bus protocol and electric requirement, and carries out signal gain according to the gain control instruction of industry control unit output;
Described conditioning plate control module, for distributing control by the signal of wave generating unit output according to the control command of industry control unit.
Further, described signal condition unit comprises over-current detection module, and over-current detection module detects outputing to the data of equipment under test, if surpassed, sets amplitude, and notice industry control unit stops fault and injects, and realizes the protection to equipment under test.
Preferably, described signal condition module comprises AFDX interface signal conditioning module, RS232 signal condition module, ARINC429 interface signal conditioning module, power fail conditioning module and 1553 signal condition modules, realizes the communication protocol requirement of different bus signal and the electrical specification requirement of electric requirement and non-bus signals.
Another object of the present invention is to provide a kind of fault filling method for avionics system Gernral Check-up, comprise the following steps:
A, industry control unit inject type according to man-machine interface to various faults and select, call different faults data-interface model and carry out protocol encapsulation and generate Wave data and deliver to wave generating unit by pci bus, and by RS232 bus to signal condition unit distribution control command and the parameter configuration of signal and the parameter configuration of interference;
B, wave generating unit are received Wave data and are resolved by pci bus, and buffer memory Wave data, carries out digital-to-analog conversion to Wave data, and all kinds of analog signal waveforms of generation and the data model of interference waveform output to signal condition unit;
C, signal condition cell processing receive control command and the parameter configuration of signal and the parameter configuration of interference of industry control unit distribution, also receive the various types of signal waveform of wave generating unit and the data model of interference waveform simultaneously, generation meets the data of the electrical specification requirement of bus protocol and electric requirement and non-bus signals, and is injected into tested equipment by corresponding connector.Further, if also comprise the data of output in described step C, surpass to set amplitude, signal monitoring module by examinations to and notify industry control unit to stop fault and inject, the protection of realization to equipment.
The present invention is by the use of Fault Insertion Equipment, according to prior selected fault model, adopt certain strategy to think fault is introduced in system under test (SUT), by observation and analysis system, in the behavior being injected under failure condition, can provide for experimenter the evaluation result of required quantitative and qualitative analysis.The test of injecting by fault, can find product design design defect in the product development stage, and the reliability of system is provided.
Accompanying drawing explanation
Fig. 1 is Fault Insertion Equipment hardware structure block diagram;
Fig. 2 is the block architecture diagram of signal condition unit;
Fig. 3 is the Organization Chart of power fail injection module;
Fig. 4 is the software architecture block diagram that ARINC429 fault is injected;
Fig. 5 is the hardware structure figure that RS232 fault is injected
Specific implementation
Below in conjunction with accompanying drawing, provide embodiments of the present invention, to describe technical scheme of the present invention in detail.
Fig. 1 is the general frame figure of Fault Insertion Equipment of the present invention.The present invention mainly realizes the simulated failure input to equipment under test, the electric signal that is mainly simulated failure is carried out fault injection, mainly comprise following fault Injection Signal: the fault of power supply is injected, the fault of 1553 signals is injected, ARINC429 fault-signal injects, AFDX fault-signal injects, and RS232 fault-signal injects and the stack of undesired signal is injected.This equipment adopts the form of man-machine interface, can inject type to various faults and select, when selecting a certain fault mode, by parameter configuration and the order distribution at main interface, the type data-interface is called, by resolving the data protocol bag from bottom, and package according to different interface protocols, after protocol encapsulation completes, just can carry out waveform drawing, be presented on the editing interface of this fault injection, after having edited, by output interface, output on network interface.Therefore, realizing the selection of different faults being injected to type, is exactly in fact to call different faults data-interface model, through protocol encapsulation, waveform drawing and editor, finally outputs on tested equipment.
Industry control unit in Fig. 1 sends instruction by man-machine interface, according to man-machine interface, various faults being injected to type selects, calling different faults data-interface model carries out protocol encapsulation and generates Wave data and deliver to wave generating unit by pci bus, wave generating unit generates the time sequence information of signal according to the selection of each agreement, do the pre-service of some signals simultaneously; Data can be sent to signal adjustment unit afterwards, and signal adjustment unit is processed the data that receive again, and the signal of finally exporting as requested electric aspect is to interface connector.If amplitude surpass is set in output, overcurrent detecting device by examinations to and notify industry control unit to stop fault and inject, the protection of realization to equipment.
Wherein wave generating unit is comprised of DSP module, FPGA module, DAC module, power module and clock module, this unit major function is the interface with industry control unit, complete pci bus Data Analysis, buffer memory Wave data, to Wave data, by digital-to-analog conversion, the analog waveform of generation outputs to signal condition unit.DSP module has been mainly used in the interface between industry control unit and wave generating unit, and data buffer storage function, it is mainly to using pci bus as interface, dsp processor is selected TMS320C6416, and FLASH, SDRAM etc. are as peripheral chip, realize the processing capacity of DSP module.FPGA module major function be DSP module to interface conversion, the data buffer storage of DAC module and give DAC by data according to refresh rate undetermined and do digital-to-analog conversion, it is mainly by buffer memory RAM, asynchronous FIFO and fifo control logic chip, to realize the control function of FPGA module.DAC module major function has been the conversion of digital signal, and simulating signal is carried out to AC coupling be transferred to signal condition unit, the main process chip of DAC module is selected the AD9777 programming device of AD company, data after conversion are carried out AC coupling by centre-tapped transformer, realize the output function of DAC.Power module major function is to realize each unit that direct power supply is provided, and it,, by AC-DC power conversion chip, then becomes the required direct supply of each module by voltage stabilizing, filtering, DC-DC circuit conversion.Clock module major function is for each module provides clock input, guarantees the signal integrity of transmitting procedure.
Fig. 2 is core cell signal condition of the present invention unit, and signal condition unit is by signal coupling and distribution module, conditioning plate control module, power module, over-current detection module, AFDX interface signal conditioning module, RS232 signal condition module, ARINC429 interface signal conditioning module and discrete signal conditioning module.
Signal coupling and distribution module, be coupled to this unit by DAC output signal, and signal is distributed to the signal condition module of each interface signal under the control of conditioning plate control module;
Signal condition module, input signal is nursed one's health to conversion, make it to meet each interface requirement, the gain of signal by the waveform district of the main interface software of industry control unit by the zoom operations (amplification of amplitude is dwindled etc.) of waveform, to signal condition module output gain steering order, the amplitude of signal condition module parses industry control unit, selects different gains to control, and realizes the gain of signal and controls.
Conditioning plate control module, responsible conditioning plate is communicated by letter with industry control unit, the functions such as DAC signal distribution control and overcurrent protection.
Fig. 3 is the Organization Chart of power fail injection module, adopt Waveform Synthesis Technology, industry control unit, the synthetic waveform of needed power supply output, if do not disturbed, is exactly a constant level signal, if there is undesired signal, synthetic with the level signal of output after undesired signal digitizing, then output to wave generating unit and carry out digital-to-analog conversion, then carry out high-power amplifier by the power fail conditioning module of signal condition unit, driver output, produces needed supply voltage;
Fig. 4 is the block architecture diagram that ARINC429 fault is injected, the user interface of the UI design by industry control unit, the parameter that generates waveform is set, add and need the raw data of output to start to generate waveform, digital simulation ARINC429 frame structure is started to group bag in industry control unit, then carry out Manchester's cde and filtering, reach the data of the network physical transmission of standard, then result is stored in a buffer memory of opening in advance, UI interface generates waveform according to the data in buffer memory when generating waveform, when needs configuration output fault excited data, interference wave or increase burr as required can superpose, these signals output in the ARINC429 network of equipment under test by signal condition unit the most at last, except electrical layer being carried out to fault injection, protocol layer mistake also can be carried out reliability testing to each field, reliability testing type comprises mistake: position negate, random number, normal value are replaced, can be at random, by the time interval, by byte interval, Frame kind particular data position is replaced, maximum 4 continuous WORD are supported in the location of Frame, can carry out bit mask, frame alignment fault data is supported 4 groups, every group of 1 WORD, can carry out bit mask, the fault type capable of regulating of each group.
The software architecture that AFDX fault is injected and hardware structure and ARINC429's is basic identical, AFDX fault inject to adopt is the processing that packages of UDP/IP agreement, in industry control unit, carry out successively UDP group bag, IP organizes bag, MAC organizes bag, after protocol encapsulation completes, starts drawing waveforms, then carry out Manchester's cde and filtering, reach the data of the network physical transmission of standard; Result is stored in to one in advance in open buffer zone, in the time of output waveform, data is outputed to the FPGA module in wave generating unit, then FPGA is outputed to DAC module converts and is become analog signal output.AFDX electrical layer can injected frequency drift error, and MAC layer can inject frame gap (IFG) mistake, short lead code (short preamble) mistake, CRC (CRC) mistake, ethernet type mistake; AFDX protocol layer can inject frame length mistake, redundant sequence number (RSN) mistake, BAG mistake, VL/Port mistake, message format mistake etc.
The software architecture that MIL-STD-1553 bus failure injects and hardware structure and above-mentioned two kinds of buses basic identical, by generating MIL-STD-1553 interface data in industry control unit, in the FPGA of wave generating unit module, carry out filtering and generate the noisy signal with burr, these signals are input in the DAC module of wave generating unit, the level that is adjusted into requirement through 1553 signals of conversion output in signal regulating panel, 1553 buses that are finally coupled to test product get on.1553 bus failure output electrical layer can be carried out signal dutyfactor adjusting, and output voltage gradient regulates and bus signals noise and burr simulation, and protocol layer can postpone bus acknowledge, the simulation of the faults such as bus signals bit-errors and message replacement.
Fig. 5 is the hardware structure figure that RS232 fault is injected, RS232 fault is injected and is controlled by application interface, the generation of the generation of fault-signal, RS232 original data block, and add after parity check bit, start bit, position of rest, filtering interpolation etc. are processed in industry control unit and export to wave generating unit, DSP receives data by PCIe bus, by FPGA, control DAC output and conditioning plate control module gain control processing, finally by signal coupling and distribution module and the signal condition module output RS232 signal of signal condition unit.The fault mode of RS232 can be divided into error of transmission and data bit mistake, and error of transmission comprises that providing start bit, position of rest error pattern, data bit mistake can carry out negate, random number and normal value replaces and can carry out bit mask.
Claims (8)
1. the Fault Insertion Equipment for avionics system Gernral Check-up, comprise industry control unit, wave generating unit, signal condition unit, it is characterized in that described industry control unit injects type according to man-machine interface to various faults and selects, call different faults data-interface model and carry out protocol encapsulation and generate Wave data and deliver to wave generating unit by pci bus, and by RS232 bus to signal condition unit distribution control command and the parameter configuration of signal and the parameter configuration of interference;
Described wave generating unit is received Wave data and is resolved by pci bus, and buffer memory Wave data, carries out digital-to-analog conversion to Wave data, and all kinds of analog signal waveforms of generation and the data model of interference waveform output to signal condition unit;
Signal condition cell processing receives control command and the parameter configuration of signal and the parameter configuration of interference of industry control unit distribution, in conjunction with the various types of signal waveform of wave generating unit and the data model of interference waveform, generation meets the data of bus protocol and electric requirement, and being injected into tested equipment by corresponding connector, these data comprise bus data and interfering data etc.
2. Fault Insertion Equipment according to claim 1, is characterized in that described wave generating unit comprises DSP module, FPGA module, DAC module, power module, clock module;
Described DSP module has been used for the interface conversion resolution data between industry control unit and wave generating unit, and data buffer storage;
Described FPGA module comprises buffer memory RAM, asynchronous FIFO and fifo control logic chip, for completing DSP module to interface conversion, the data buffer storage of DAC module and giving DAC by data according to refresh rate undetermined and do digital-to-analog conversion;
Described DAC module has been used for the conversion of digital signal, and analog signal output is arrived to signal condition unit.
Described power module major function is to realize each unit that direct power supply is provided, and it,, by AC-DC power conversion chip, then becomes the required direct supply of each module by voltage stabilizing, filtering, DC-DC circuit conversion;
Described clock module major function is for each module provides clock input, guarantees the signal integrity of transmitting procedure.
3. Fault Insertion Equipment according to claim 1 and 2, it is characterized in that having in described wave generating unit 2 duplicate DAC modules of function, buffer memory RAM by FPGA module controls the passage of Wave data being delivered to corresponding DAC module, finally completes the digital-to-analog conversion of this Wave data.
4. Fault Insertion Equipment according to claim 1, is characterized in that described signal condition unit comprises signal coupling and distribution module, conditioning plate control module, power module, each signal condition module;
Described power module provides power supply guarantee for each module;
Described signal coupling and distribution module, arrive this unit by the signal coupling of wave generating unit output, and signal be distributed to each signal condition module under the control of conditioning plate control module;
Described signal condition module, nurses one's health conversion to input signal, produces the data that meet bus protocol and electric requirement, and carries out signal gain according to the gain control instruction of industry control unit output;
Described conditioning plate control module, for distributing control by the signal of wave generating unit output according to the control command of industry control unit.
5. according to the Fault Insertion Equipment described in claim 1 or 4; it is characterized in that described signal condition unit comprises over-current detection module; over-current detection module detects outputing to the data of equipment under test; if surpassed, set amplitude; notice industry control unit stops fault and injects, and realizes the protection to equipment under test.
6. Fault Insertion Equipment according to claim 4, it is characterized in that described signal condition module comprises AFDX interface signal conditioning module, RS232 signal condition module, ARINC429 interface signal conditioning module, power fail conditioning module and 1553 signal condition modules, realizes the communication protocol requirement of different bus signal and the electrical specification requirement of electric requirement and non-bus signals.
7. for a fault filling method for avionics system Gernral Check-up, comprise the following steps:
A, industry control unit inject type according to man-machine interface to various faults and select, call different faults data-interface model and carry out protocol encapsulation and generate Wave data and deliver to wave generating unit by pci bus, and by RS232 bus to signal condition unit distribution control command and the parameter configuration of signal and the parameter configuration of interference;
B, wave generating unit are received Wave data and are resolved by pci bus, and buffer memory Wave data, carries out digital-to-analog conversion to Wave data, and all kinds of analog signal waveforms of generation and the data model of interference waveform output to signal condition unit;
C, signal condition cell processing receive control command and the parameter configuration of signal and the parameter configuration of interference of industry control unit distribution, also receive the various types of signal waveform of wave generating unit and the data model of interference waveform simultaneously, generation meets the data of the electrical specification requirement of bus protocol and electric requirement and non-bus signals, and is injected into tested equipment by corresponding connector.
8. fault filling method according to claim 7, surpasses and sets amplitude if it is characterized in that also comprising in described step C the data of output, signal monitoring module by examinations to and notify industry control unit to stop fault and inject, the protection of realization to equipment.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104270211A (en) * | 2014-10-21 | 2015-01-07 | 中国航空无线电电子研究所 | Serial bus fault injection method |
| CN105223941A (en) * | 2014-06-23 | 2016-01-06 | 中航商用航空发动机有限责任公司 | Hardware is in loop fault injected system |
| CN106990771A (en) * | 2017-01-04 | 2017-07-28 | 中南大学 | Fault filling method and system |
| CN107219843A (en) * | 2017-06-19 | 2017-09-29 | 哈尔滨工业大学 | The fault-signal analogue means of MIL STD 1553B bus nodes based on arbitrary-function generator |
| CN107947959A (en) * | 2017-10-13 | 2018-04-20 | 北京航空航天大学 | A kind of IMA system total failure management systems based on ASAAC systems |
| CN108983141A (en) * | 2018-05-07 | 2018-12-11 | 浙江涵普电力科技有限公司 | The DC voltage and ripple voltage synthesizer of direct current energy meter |
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| CN112380084A (en) * | 2020-12-05 | 2021-02-19 | 中国人民解放军32181部队 | Fault injection and simulation verification method |
| CN113009262A (en) * | 2021-03-08 | 2021-06-22 | 中国大唐集团科学技术研究院有限公司华中电力试验研究院 | Method for judging interference type of Profibus-DP bus |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012010488A (en) * | 2010-06-25 | 2012-01-12 | Hitachi Ltd | Motor system, power converter, and control method for power converter |
| CN102523133A (en) * | 2011-12-07 | 2012-06-27 | 中国航空无线电电子研究所 | Automatic test equipment of performance parameter of multiplex data transmission bus and test method |
| US20130013969A1 (en) * | 2011-05-20 | 2013-01-10 | Whizchip Design Technologies Pvt. Ltd. | Bus transaction monitoring and debugging system using fpga |
| CN103019902A (en) * | 2012-12-13 | 2013-04-03 | 中国航空无线电电子研究所 | Automatic testing device and automatic testing method of ARINC 429 bus signal performance parameters |
| CN103033210A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Simulation testing system of electronic flight instrument system |
| CN103399771A (en) * | 2013-08-12 | 2013-11-20 | 中国航空无线电电子研究所 | Multi-DSP bootstrapping loading system based on serial high-speed interface bus and method thereof |
-
2013
- 2013-12-03 CN CN201310642372.XA patent/CN103631255B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012010488A (en) * | 2010-06-25 | 2012-01-12 | Hitachi Ltd | Motor system, power converter, and control method for power converter |
| US20130013969A1 (en) * | 2011-05-20 | 2013-01-10 | Whizchip Design Technologies Pvt. Ltd. | Bus transaction monitoring and debugging system using fpga |
| CN102523133A (en) * | 2011-12-07 | 2012-06-27 | 中国航空无线电电子研究所 | Automatic test equipment of performance parameter of multiplex data transmission bus and test method |
| CN103019902A (en) * | 2012-12-13 | 2013-04-03 | 中国航空无线电电子研究所 | Automatic testing device and automatic testing method of ARINC 429 bus signal performance parameters |
| CN103033210A (en) * | 2012-12-13 | 2013-04-10 | 中国航空无线电电子研究所 | Simulation testing system of electronic flight instrument system |
| CN103399771A (en) * | 2013-08-12 | 2013-11-20 | 中国航空无线电电子研究所 | Multi-DSP bootstrapping loading system based on serial high-speed interface bus and method thereof |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105223941A (en) * | 2014-06-23 | 2016-01-06 | 中航商用航空发动机有限责任公司 | Hardware is in loop fault injected system |
| CN105223941B (en) * | 2014-06-23 | 2018-01-02 | 中国航发商用航空发动机有限责任公司 | Hardware is in loop fault injected system |
| CN104270211A (en) * | 2014-10-21 | 2015-01-07 | 中国航空无线电电子研究所 | Serial bus fault injection method |
| CN106990771A (en) * | 2017-01-04 | 2017-07-28 | 中南大学 | Fault filling method and system |
| CN106990771B (en) * | 2017-01-04 | 2019-06-28 | 中南大学 | Fault filling method and system |
| CN107219843A (en) * | 2017-06-19 | 2017-09-29 | 哈尔滨工业大学 | The fault-signal analogue means of MIL STD 1553B bus nodes based on arbitrary-function generator |
| CN107219843B (en) * | 2017-06-19 | 2019-02-22 | 哈尔滨工业大学 | MIL-STD-1553B bus node fault-signal simulator |
| CN107947959A (en) * | 2017-10-13 | 2018-04-20 | 北京航空航天大学 | A kind of IMA system total failure management systems based on ASAAC systems |
| CN109696899A (en) * | 2017-10-20 | 2019-04-30 | 中国商用飞机有限责任公司 | A kind of dedicated quality synthesis evaluation system of aircraft ARINC429 bus |
| CN109696899B (en) * | 2017-10-20 | 2022-02-18 | 中国商用飞机有限责任公司 | Special quality comprehensive evaluation system for aircraft ARINC429 bus |
| CN108983141A (en) * | 2018-05-07 | 2018-12-11 | 浙江涵普电力科技有限公司 | The DC voltage and ripple voltage synthesizer of direct current energy meter |
| CN110873831A (en) * | 2019-12-03 | 2020-03-10 | 中国航空综合技术研究所 | Frequency fault injector for medium-low frequency sinusoidal signals |
| CN110873831B (en) * | 2019-12-03 | 2021-10-08 | 中国航空综合技术研究所 | Frequency fault injector for medium-low frequency sinusoidal signals |
| CN112034296A (en) * | 2020-09-27 | 2020-12-04 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Avionics fault injection system and method |
| CN112380084A (en) * | 2020-12-05 | 2021-02-19 | 中国人民解放军32181部队 | Fault injection and simulation verification method |
| CN112380084B (en) * | 2020-12-05 | 2024-03-26 | 中国人民解放军32181部队 | Fault injection and simulation verification method |
| CN113009262A (en) * | 2021-03-08 | 2021-06-22 | 中国大唐集团科学技术研究院有限公司华中电力试验研究院 | Method for judging interference type of Profibus-DP bus |
| CN113009262B (en) * | 2021-03-08 | 2023-11-17 | 中国大唐集团科学技术研究院有限公司华中电力试验研究院 | Profibus-DP bus interference type discriminating method |
| CN115079671A (en) * | 2022-06-30 | 2022-09-20 | 哈尔滨工业大学（威海） | Fault injection system of serial multi-bus |
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